Accession Number : AD0772736

Title :   Program to Improve the Fracture Toughness and Fatigue Resistance of Aluminum Sheet and Plate for Airframe Applications.

Descriptive Note : Final technical rept. 1 Jul 72-1 Jul 73,

Corporate Author : BOEING COMMERCIAL AIRPLANE CO SEATTLE WASH

Personal Author(s) : Hyatt,Michael V.

Report Date : SEP 1973

Pagination or Media Count : 108

Abstract : Mechanical, fracture, smooth and notched fatigue, fatigue crack growth rate, and exfoliation corrosion tests were conducted to evaluate the effects of the various thermomechanical treatments. For comparison purposes, data were obtained on the commercial alloys 2024-T3, 7075-T6, 7475-T61, 7475-T761. In addition, a few TMTs on the commercial 7475 alloy were evaluated. (Modified author abstract)

Descriptors :   *Aluminum alloys, *Fracture(Mechanics), Fatigue(Mechanics), Thermomechanics, Toughness, Exfoliation, Crack propagation, Microstructure, Airframes

Subject Categories : Aircraft
      Properties of Metals and Alloys

Distribution Statement : APPROVED FOR PUBLIC RELEASE